Turbine wheel exducer structure



Jan. 26, 1965 w. D. WHITAKER TURBINE WHEEL EXDUCER swaucwuss Original Filed April 21. 1958 5 Sheets-Sheet 1 Fiyl ATTORNEY v J -T 1965 w. D. WHITAKER 3,167,301

TURBINE WHEEL EXDUCER STRUCTURE Criginal Filed April 21/1958 3 Sheets-Sheet 2 INVENTOR.

WILL/AM D. WHITAKER A TTORNE Y W. D. WHITAKER TURBINE WHEEL EXDUCER STRUCTURE 3 Sheets-Sheet 3 Jan. 26, 1965 Original Filed April 21. 1958 l I l 6 I 42 II INVENTOR.

WILL/AM D. WHITAKER A Tron/v6 r United States Patent 0.

This invention relates to bladed wheels for use with elastic fluids and more particularly to a turbine or impeller wheel having means for damping vibration of its blades.

' This application is a true division of my copending application, Serial No. 729,734, filed April 21, 1958, now

, Patent No. 3,065,954, issued Nov. 27, 1962, which in turn is a division of application Serial No. 379,561, filed September 11, 1953, now Patent No. 2,859,933, issued November 11, 1958, entitled Turbine Wheel Exducer Structure.

-During operation of conventional turbine or impeller wheels, cracking of the blades sometimes occurs as the result of fatigue failure occasioned by vibrational stresses.

When blades of a turbine wheel are permitted to vi brate at a resonant frequency thereof, the amplitude of the natural frequency of vibration increases to such an extent that fatigue cracking may result. This condition is particularly dangerous when it occurs in a wheel operating at high rotational speed. Various prior art devices have been employed in an attempt to alleviate the effects of vibration on turbine wheel blades. Such devices have embodied preloaded, axially abutted blades which eventually relax due to the effects of high temperatures, and consequently become inoperative. Vibration damping devices such as ball bearing blade couplers have also been contemplated. Furthermore, rivets loosely supported in Wheel blades are known to be useful in blade vibration damping. The two latter devices, however, have insufiicient bearing area upon the blades, and are therefore subject to short life, and furthermore, are very dangerous when they fail due to high centrifugal loads acting thereon. It is accordingly recognized that any device employed for damping of vibration in the blades of turbine or compressor wheels must be simple and durable even at high rotational speeds, and also must be economical to produce.

It is an object of this invention to provide a turbine or compressor wheel having separate hub portions, each being provided with extending blades engaging the blades ofthe adjacent hub portion in axially overlapping relationship, whereby the wheel structure is simple to manufacture and also very durable in operation.

Another object of the invention is to provide means for damping vibrational stresses which may occur in rotating wheel blades, which means is very simple to assemble and maintain in proper operating condition.

A further object of the invention is to provide a bladed wheel for use with elastic fluids having a plurality of individual hub-sections, each carrying blades which over lap corresponding adjacent hub blades near the extremities thereof, whereby the blades are effectively restrained against excessive vibration at their natural frequencies. Another object of the invention is to provide, for use in a turbine or compressor, a bladed wheel having a plural ty of bladed hub portions, adjacent hub blades of which overlap other blades substantially along the direction of rotation thereof, whereby motive forces applied to the blades by the fluid cause them to firmly engage and damp vibration of each other.

Sitil another object of the invention is to provide a bladed wheel wherein overlapping blade portions extend over an area sufficient to provide a durable damping structure.

Still another object of the invention is to provide means for reducing combined thermal and vibrational stresses in bladed wheels.

Another object of the invention is to provide a bladed wheel for centripetal operation having gas conducting passages within the wheel hub to permit more rapid heatlng thereof, which tends to reduce the radial temperature gradient which may be created in the wheel during initial heating of its back disk.

A further object of the invention is to provide a bladed Wheel having a thermally responsive ring positioned near the back disk thereof, adapted to thermally influence the wheel and thereby reduce the radial temperature gradient from the periphery to the hub thereof durin cycles of heating and cooling of the wheel. 5

Another object of the invention is to provide a radially bladed wheel having novel means for reducing the radial temperature gradient in the back disk thereof.

These and other objects will be apparent from the following specification and accompanying drawings in which:

FIG. 1 is a fragmentary axially sectional view taken on line 1-4. of FIG. 2 of an elastic fluid centripetal turbine wheel shown positioned in a conventional turbine housing and having thermal gradient controlling means, together with wheel blade vibration damping means;

FIG. 2 is a fragmentary view taken on line 22 of FIG. 1 showing portions broken away and in section; FIG. 3 is a fragmentary sectional view taken from. line 33 of FIG. 1;

FIG. 4 is a perspective view of a wheel hub connection pin utilized in the wheel structure of FIG. 1;

FIG. 5 is a perspective view of a bladed wheel having modified blade damping means thereon;

- FIG. 6 is a sectional view of the wheel shown in FIG. 5 disposed in a conventional turbine housing similar to that shown in FIG. 1; and

FIG. 7 is a fragmentary sectional view taken from line 77 of FIG. 5 and showing the overlapping blade vibration damping structure of the wheel of FIG. 5.

A turbine wheel 10 of centripetal configuration, as shown in FIG. 1 of the drawings, is provided with a back disk 11 gradually tapering in cross section from the hub to the periphery of the wheel. Integral with the back disk 11 are substantially radially extending blades 12. The back disk 11, at its hub portion, is provided with a hollow cylindrical extension 13 engaged telescopically by a hollow cylindrical connection portion 14 of a separate hub section 15 having integral blades 16. The blades 12 and 16 overlap and bear upon each other, in the direction of rotation thereof, as shown best in FIGS. 1 and 3. As illustrated in FIG. 3, the blades 12 and 16 overlap each other in a plane of rotation Aat Patented Jan. 26, 1965 o their engagingedge surfaces 17 and 18, respectively, at an angle'of substantially 45 degrees.

It will benoted that the surface 17 18 of the blades 16 in the direction of rotation, which is e indicated by the arrow C. The overlapping portionsof of the blade 12, as: shown in FlGpb, provides an abutment for the surface 7 aiezaoi v greater than that ofvthelcorresponding adjacent annular portion ofthe wheel back disk. The ring, therefore, as-

the blades 12 and 16 atiord sufiicient bearing area to in' e sure durability of the structures under vibration and also to provide efficient damping engagement of the blades of V 7 both hub portions 11 and 15. Due'to the proportional relationship of the mass and structureof the blades 121and sists in reducing the thermal gradient from the periphery v of the wheeltoits' hub portion, whichwould otherwise occur during starting or stopping of the turbine; The ring 2 'is pro vided with annular grooves 2% and Sil in which annular ribs 12b and 12a of the back'disk 11 are disposed. The cooperative relationshipof the grooves 2av and as and er the ribs 1% and 120 provides a labyrinth seal intermediate the back disk '11 and the ring 28 which prevents excessive flow ,of 'hot gas inwardly along the backside of the'wheel toward its axis. The ring 28 is provided with an annular, rearwardly extending boss portion 31 into which'are screw-threaded bolts 32 which secure the ring 28 to a side Wall 33 secured to the turbine casing '27, I I f In operation, hot gas flows through-the nozzles 26 and intermediatetheblades 12 and 16. Gas, traveling "at high with recesses 19 and 20, respectively, which communicate 7 with each 'other'and with the passages between adjacent blades 12 and 16. The recesses 19 and 2%}, therefore, provide openings communicatng with the passages between the blades and with the telescopically connected extensions 7 13, and 140i the back disk ll'and hub 15, respectively.-

As shown in FIG. 2, the communicating recess portions p 19 and 2% form openings 22 which are disposed between the blades of the wheel and which are in alignment with three pins 21. Before assembly of the telescopic connec-v a lt willv be obvious-that the engaged relationship of the, V blades 12 and 16 is applicable to' the wheel structures of tions 13 and 14, the pins 21 are inserted in openings 23 in the telescopic cylindrical extension 13; then the extensions 13 and 14 are telescopically engaged by axialmovement of the hub 15 relative totheback disk 11, whereupon the'openings 23 are aligned with openings 24 in the cylindrical telescopic extensionl of the hub 1 5, permitting a tool to be inserted through one of the openings 22 and through an openingll for driving each pininto anoppositeopening 24'aligned therewith.

The pins 21,- as shown'in FIG. 4, re provided with' slight projections 25 which are swaged by a driving fit thereof into the telescopic extensions 13 and'14, whereby r the pins '21 are securely fixed inposition, as'shown in FIG. 1. The openings velocity intermediate'the bladesais turned on the concave surfaces 16a of the blades 16. Such turning of the gases creates thrust on the blades 16 in the direction ofirotation, as indicated ;by:the arrowCin'FIG. 3. When the blades 16 are thrust in the direction of the 'arrow C, they intimately engage the bladesl12 in the direction of rotation. The, blades 12 and lti each vibrate at different natural frequencies and during engagement ortheir sur faces 17 and 18,vrespective'ly, theytend-to-dampenvibration ofeachother, thereby preventinga resonant con dition in which the amplitude might reach damaging proportions.

compressors whereinblade vibration damping may be necessary. i

g the nozzles 26 causes the PQI'lPllfiIYOf the back disk 11 When the turbine'is started, the iflow of hot gas through to be heated quite rapidly. The ring' 28, disposed in close proximity to-itheiback disk 11,:tends to absorb heat tfromthe'peripheral'back disk portion, at the same time 22 intermediate the wheel blades permit."

access of hot gases to' the recessedportions 19 and'29 communicating with therelatively thickhub portion of the back disk 11 near itsaxis." Suchflow of hot gases,-durback disk 11 in orderto reduce-the'the'rmal gradient between the periphery tand the axis of the back disk..

56 ingstarting of the turbine, heats thehubtportion of the turbine.

portion of thewheel. cry of the back disk 11v is prevented by the ring 23. The

thus reducingits tendency toyheat faster than the hub portion. .The hub por'tion of the back disk near the axis of'the wheel is heatedby gas entering the openings22, thus further reducing l-the initial thermal gradient from the periphery QfthC-Wl'llitO its'hub portion. ,Such reduction in the initial thermal gradient materially reduces thermal stresses inthe black disk 11 during starting of the,

when theaflow'oflhot gas through the nozzles 26 is shut oif, the relatively'thinperipheral. portion of the back disk 11 would tend to cool more rapidly than the hub,

Such'rapidcooling of the periphring radiates heatto, theperiphe'ral back disk portion and The turbinewheel, composedot-the back disk 11, hubf:

' 15,iand the blades 12 and 16, 'iseof the centripetal type wherein the blades. 16 are curved, as shown in FIG. 3...

The blades 16 are provided with concave surfaces, 16a adapted to be contacted by the gas flowing in the' direction indicated by arrows. B in FIGVI. The peripheral'portions 12a of the blades of the turbine wheelare' ar consequently thehub portion has suflicient time to cool toa certamextentbefore thetemperature' of the peripheralback disk portion has been reducedto a value which [would causecritical internal stresses. Thus, 'during the ranged to rotate in close relation to conventional sta tionary nozzle vanes 26. t I 7 Positioned internally'of a turbine casing 271is a hired ring 28'which is disposed in close proximity to the side of the back disk 11 opposite the blades 12,, all as shown best in FIG. 1.; Thelring 28 iscOntacted byhot gas which 1 spills over the periphery of the turbine wheel. The mass of the ringf28 is sufiicient to provide for heat exchange with adjacent portionsof the back disk 11 d'uringheating I and cooling of the turbine wheel. The ring 28, extends inwardly from the periphery of the wheel adistance of approximately one third or. more of the radius thereof; The peripheral portion of the back disk 11 isconsiderr' ably thinner than its hub portion, and hencethe mass of the outer annular portion of the ring 28 is preterably' nade I cooling period, the temperature gradient in thezturbine wheel from itsperiphery-to its hub portion is'materially reduced. It is believed that the ring 28, reducing the thermal; stresses in the wheel, and the vibration damping structure heretofore described, cooperate to prevent cracking of thejwheel blades and theback disk.

. In the modified form of the mvent on; as shown in FIGS.

5, 6 and 7; the turbine wheel is provided with aback disk 34 having i'ntegral blades 35 arranged in overlapping relation with blades 36 on a blade hub member 37. The

V hub 37 is provided with a concentric recess portion 38 surrounding an extending concentric stub 39 of the back disk '34; I A bolt 41' is screw-threaded in athreaded concentric hole 40 in the back disk 34. The bolt 41 exerts axial clamping force on the. hubt37 for retaining it securely connected to the back disk 34. Adjacent'blades 35 and 36 are arranged in oifset overlapping relationship to each other,"

as shown best in F IGs- S and '7. The ofisetoverlapping portions of the blades 35 and 36 are disposed near the outer extremities thereof; thus, the blades 36' overlap the blades 35 along approximately half their length. As shown in FIG. 6, the. blades, 35 and 36 overlap between the-points 42 and. 43. Adjacent edges 44 and 45 of the blades 35 and 36, respectively, are disposed at an acute angle to each other to, provide, for offset overlapped arrangement. The blades 36 are provided with concave surfaces 46 adapted to be contacted by gas flowing between the blades. The flow of gas creates thrust in the direction of rotation, as shown by the arrow D in FIG. 7, forcing the blades 36 against the blades 35 at their overlapping edges.

A ring 47 is positioned in close proximity to the back disk 34, as shown in FIG. 6. Ring 47 is similar in structure and operates in the manner of the ring 28 hereinbefore described and shown in FIG. 1.

In the operation of the modified form of the invention shown in FIGS. 5, 6 and 7, gas flows through the turbine wheel and around the ring 47 in a similar manner to that hereinbefore described and shown in FIGS. 1, 2 and 3. When gas flows between the blades 35 and against the concave surfaces 46 of the blades 36, the overlapping portions of the blades 35 and 36, as shown in FIG. 7, are engaged. Such engagement is caused by thrust of the gas on the blades 36 which forces them in the direction of rotation and into engagement with the blades 35, thus damping vibration.

I claim:

1. A centripetal turbine wheel for operation with hot fluids having:

(a) a back disk, the thickness of said back disk increasing from the outer extremities to the middle thereof;

([2) blades on one side of said back disk;

(c) nozzle means outwardly of said Wheel;

(d) a casing for said wheel and said nozzle means; and

(e) a heat absorbing and storing ring in close proximity to said back disk at the opposite side thereof from said blades, the said ring having an outer peripheral portion the mass of which is greater than the corresponding annular outer peripheral portion of said back disk.

2 A centripetal turbine wheel for operation with hot gas having:

(a) a back disk, the thickness of said back disk increasing from the outer extremities to the middle thereof;

(b) blades on one side of said back disk;

() nozzle means outwardly of said wheel;

(0.) a casing for said wheel and said nozzle means; and

(e) a heat absorbing and storing ring in close proximity to said back disk at the opposite side thereof from said blades, said ring being substantially equal in diameter to said back disk and extending from the periphery toward the axis of said wheel for a distance equal to approximately one-third the radius of the wheel, the outer peripheral portion of the ring having a mass greater than the corresponding outer peripheral portion of said disk.

3. A centripetal turbine wheel for operation with hot gas having:

(a) a back disk, the thickness of said back disk increasing from the outer extremities to the middle thereof;

(b) blades on one side of said back disk;

(c) nozzle means outwardly of said wheel;

(d) a casing for said wheel and said nozzle means;

(e) a heat absorbing and storing ring in close proximity to said back disk at the opposite side thereof from said blades; and

(f) a hub formed with said back disk and having means between said blades extending into said hub for admitting hot gas thereinto so that the thermal gradient from the periphery to the hub is reduced by the hot gas conducted into said hub.

4. In a hot gas operated turbine:

(12) a centripetal wheel having a back disk, the thickness of which increases from the periphery toward the center;

(b) spaced blades projecting from the front face. of said back disk and providing gas passages in. said wheel;

(0) nozzle means disposedadjacent the periphery of said wheel for directing hot gases against said blades to effect rotation of said Wheel;

(d) a heat absorbing and storing ring disposed in close proximity to the back face of said disk, said ring having an outer peripheral portion the mass of which is greater than the mass of the corresponding annular outer peripheral portion of said back disk; and

(e) an annular seal between the intermediate portion of said ring and said wheel to limit the flow of hot gases through the space between the wheel and ring toward the axis of the wheel.

5. In a hot gas operated turbine:

(at) a centripetal wheel having a back disk, the thickness of which increases from the periphery toward the center;

(b) spaced blades projecting from the front face of said back disk and providing gas passages in said wheel;

(0) nozzle means disposed adjacent the periphery of said wheel for directing hot gases against said blades to eifect rotation of said wheel;

(at) a heat absorbing and storing ring disposed in close proximity to the back face of said disk, said ring having an outer peripheral portion the mass of which is greater than the mass of the corresponding annular outer peripheral portion of said back disk; and

(e) an annular labyrinth seal between the intermediate portion of said ring and said wheel to limit the flow of hot gases through the space between the Wheel and ring toward the axis of the wheel.

6. In a hot gas operated turbine:

(a) a centripetal wheel having a back disk the thick ness of which increases from the periphery toward the center;

(b) spaced blades projecting from the front face of said back disk and providing hot gas passages in said wheel;

(0) nozzle means disposed adjacent the periphery of said wheel for directing hot gases against said blades to effect rotation of said wheel;

(d) a heat absorbing and storing ring in close proximity to said back disk at the opposite side thereof from said blades, said ring being substantially diametrically equal to said back disk and extending from the periphery toward the axis of said wheel substantially one-third of the radius of the wheel, said ring having an outer peripheral portion the mass of which is greater than the mass of the corresponding annular outer peripheral portion of said back disk; and

(e) seal means between the intermediate portion of said ring and said wheel to limit the flow of hot gases through the space between the Wheel and ring toward the axis of the wheel.

7. In a hot gas operated turbine:

(11) a centripetal wheel having a back disk the thickness of which increases from the periphery toward the center;

(b) spaced blades projecting from the front face of said back disk and providing gas passages in said wheel;

(c) nozzle means disposed adjacent the periphery of said wheel for directing hot gases against said blades to effect rotation of said Wheel; and

(d) a heat absorbing and storing ring in close proximity to said back disk at the opposite side thereof from said blades, said ring being substantially diametrically ring being substantially uniform throughoutits radial Width and greater than thethickness of the back disk 2 at its outer periphery while thinner than the correspending portion ofthe back disk at the inner diameterrof the ring, the mass of the outer peripheral portion. of thering being greater than the massof the adjacent peripheral portion f said back disk.

Reierences Cited in the file of this patent UNITED STATES PATENTS.

v McVeigh Dec. 15,1953 Angell -Q. Feb. 3, 1955 T Angell et a1 June 12, 1956 Grey Feb. 11, 1958 Kohlrnann et'al. July 21, 1953 Egli Nov. 18, 1958 

1. A CENTRIPETAL TURBINE WHEEL FOR OPERATION WITH BOT FLUIDS HAVING: (A) A BACK DISK, THE THICKNESS OF SAID BACK DISK INCREASING FROM THE OUTER EXTERIMITIES TO THE MIDDLE THEREOF; (B) BLADES ON ONE SIDE OF SAID BACK DISK; (C) NOZZLE MEANS OUTWARDLY OF SAID WHEEL; (D) A CASING FOR SAID WHEEL AND SAID NOZZLE MEANS; AND (E) A HEAT ABSORBATING RING IN CLOSE PROXIMITY TO SAID BACK DISK AT THE OPPOSITE SIDE THEREOF FROM SAID BLADES, THE SAID RING HAVING AN OUTER PERIPHERAL PORTION THE MASS OF WHICH IS GREATER THAN THE CORRE- 